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Actuators
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Advanced Actuators for Aerospace Systems
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Advanced Actuators for Aerospace Systems

A special issue of Actuators (ISSN 2076-0825). This special issue belongs to the section "Aircraft Actuators".

Deadline for manuscript submissions: closed (15 November 2022) | Viewed by 17686

Special Issue Editor

Prof. Dr. Ronald M. Barrett

E-Mail Website
Guest Editor
Adaptive Aerostructures and Aircraft Design Laboratories, The University of Kansas, 2120 Learned Hall, Lawrence, KS 66045, USA
Interests: adaptive aerostructures; enhancement of transportation related technologies; missiles and munitions

Special Issue Information

Dear Colleagues,

This Special Issue is devoted to coverage of advanced actuators and their associated power delivery and control systems for aerospace vehicles, systems, and sub- and super-systems. This Special Issue will include both endoatmospheric and exoatmospheric actuator classes for vehicles as small as subscale munitions, microsats, and microdrones to jumbo jets and solar panel deployment mechanisms. Papers covering primary and secondary flight control, undercarriage extension, and retraction, as well as active flutter suppression, vibration mitigation, launch load accommodation, mission package deployment, and staging actuators are sought. Advanced approaches using pneumatics, electrostatics, electrohydrostatic, modern ultra-high-pressure hydraulics, rare-earth rotary and linear motors, shape-memory alloys, and piezoelectric and other classes of adaptive materials are of interest.

Prof. Dr. Ronald M. Barrett
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Actuators is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • aerospace actuator
  • flight control
  • electrohydrostatic
  • pneumatic
  • hydraulic
  • adaptive
  • smart
  • active
  • piezoelectric

Published Papers (7 papers)

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Research

23 pages, 2921 KiB  
Article
A Preliminary Design Method of High-Power Electro-Hydrostatic Actuators Considering Design Robustness
by Tuanhui Guo, Xu Han, Tatiana Minav and Yongling Fu
Actuators 2022, 11(11), 308; https://0-doi-org.brum.beds.ac.uk/10.3390/act11110308 - 27 Oct 2022
Cited by 2 | Viewed by 1509
Abstract
Electro-hydrostatic actuators (EHAs) are expanding their application fields due to their combined advantages of electric and hydraulic actuation. However, the control performance, the weight, and the efficiency turn out to be more challenging requirements when the EHA power level increases to over 30 [...] Read more.
Electro-hydrostatic actuators (EHAs) are expanding their application fields due to their combined advantages of electric and hydraulic actuation. However, the control performance, the weight, and the efficiency turn out to be more challenging requirements when the EHA power level increases to over 30 kW. Therefore, a preliminary design dedicated to trading off the system-level EHA performance based on multi-domain coupling analysis is necessary considering the comprehensive performance requirements and the parameter uncertainties. However, the existing methods are deficient in responding to all these design challenges. In this paper, an EHA preliminary design method is proposed to achieve the optimum system-level performance with robustness. First, the design parameters are analyzed and selected. Second, an optimization design of EHAs is realized by developing multi-disciplinary performance simulation models. The robustness is also considered during the optimization design. Third, the optimization results are evaluated by a specifically built EHA model, which realizes high fidelity than the models used for optimization. As a result, the general high-power EHA requirements are fully considered during the preliminary design and an optimum EHA performance is achieved. The proposed method is demonstrated in a design case of a 30 kW EHA for aerospace applications, which achieved the optimum performance of 8 Hz bandwidth and 69.92 kg weight. The preliminary design results also outline the input information for the following detailed design. Therefore, the proposed method demonstrated its applicability for delivering robust EHA design results for engineering applications. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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18 pages, 12319 KiB  
Article
Overview of the SmartX Wing Technology Integrator
by Roeland De Breuker, Tigran Mkhoyan, Nakash Nazeer, Vincent Stuber, Xuerui Wang, Iren Mkhoyan, Roger Groves, Sybrand van der Zwaag and Jurij Sodja
Actuators 2022, 11(10), 302; https://0-doi-org.brum.beds.ac.uk/10.3390/act11100302 - 20 Oct 2022
Cited by 3 | Viewed by 2563
Abstract
This article describes the challenges of integrating smart sensing, actuation, and control concepts into an over-sensed and over-actuated technology integrator. This technology integrator has more control inputs than the expected responses or outputs (over-actuated), and its every state is measured using more than [...] Read more.
This article describes the challenges of integrating smart sensing, actuation, and control concepts into an over-sensed and over-actuated technology integrator. This technology integrator has more control inputs than the expected responses or outputs (over-actuated), and its every state is measured using more than one sensor system (over-sensed). The hardware integration platform is chosen to be a wind tunnel model of a low-speed aircraft wing such that it can be tested in a large university-level wind tunnel. This hardware technology integrator is designed for multiple objectives. The nature of these objectives is aerodynamic, structural, and aeroelastic, or, more specifically; drag reduction, static and dynamics loads control, aeroelastic stability control, and lift control. Enabling technologies, such as morphing, piezoelectric actuation and sensing, and fibre-optic sensing are selected to fulfil the mentioned objectives. The technology integration challenges are morphing, actuation integration, sensor integration, software and data integration, and control system integration. The built demonstrator shows the intended level of technology integration. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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26 pages, 7871 KiB  
Article
Double Redundancy Electro-Hydrostatic Actuator Fault Diagnosis Method Based on Progressive Fault Diagnosis Method
by Hai-Tao Qi, Dong-Ao Zhao, Duo Liu and Xu Liu
Actuators 2022, 11(9), 264; https://0-doi-org.brum.beds.ac.uk/10.3390/act11090264 - 13 Sep 2022
Cited by 3 | Viewed by 2442
Abstract
The electro-hydrostatic actuator (EHA) is the key component of most electric aircraft, and research on its fault diagnosis technology is of great significance to improve the safety and reliability of aircraft flight. However, traditional fault diagnosis methods only focus on partial failures and [...] Read more.
The electro-hydrostatic actuator (EHA) is the key component of most electric aircraft, and research on its fault diagnosis technology is of great significance to improve the safety and reliability of aircraft flight. However, traditional fault diagnosis methods only focus on partial failures and cannot completely diagnose the whole EHA system. In this paper, the progressive fault diagnosis method (PFDM) is proposed for overall diagnosis of whole EHA system, which can be divided into four levels for health detection and fault diagnosis of the overall EHA system. PFDM combines fault diagnosis methods based on Kalman filter, threshold, logic, and EHA system analysis model to diagnose the whole EHA system layer by layer. At the same time, in order to ensure the normal operation of the EHA system after fault diagnosis, double redundancy design is creatively carried out for the EHA system to facilitate system reconstruction after fault detection. It can be continuously modified according to different EHA system parameters and measured signals to improve the accuracy of fault diagnosis. The experimental results show that PFDM can accurately locate and identify 22 faults of the double redundancy EHA system by using the accurate EHA system mathematical model. PFDM improves the fault diagnosis response time to 4 ms, greatly improving the safety and reliability of the double redundancy EHA system. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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17 pages, 9518 KiB  
Article
High-Rate, High-Precision Wing Twist Actuation for Drone, Missile, and Munition Flight Control
by Ronald Barrett-Gonzalez and Nathan Wolf
Actuators 2022, 11(8), 239; https://0-doi-org.brum.beds.ac.uk/10.3390/act11080239 - 21 Aug 2022
Cited by 3 | Viewed by 1805
Abstract
This paper covers a new actuation and deflection controller configuration for high-aspect-ratio wings used on subsonic drones, missiles, and munitions. Current approaches to the flight control of these aircraft have unearthed challenges with friction, stiction, slop, bandwidth, and thick boundary layer nonlinearities, which [...] Read more.
This paper covers a new actuation and deflection controller configuration for high-aspect-ratio wings used on subsonic drones, missiles, and munitions. Current approaches to the flight control of these aircraft have unearthed challenges with friction, stiction, slop, bandwidth, and thick boundary layer nonlinearities, which degrade flight control accuracy—especially in terminal flight phases. The approach described in this paper uses directionally attached piezoelectric (DAP) actuators to actively twist a high-aspect-ratio wing for flight control. The DAP actuators were modeled analytically and computationally using linear finite element modeling. A 3″ (7.62 cm) chord × 15″ (38.1 cm) semispan rectangular wing with an NACA 0012 profile was built and structurally tested, demonstrating excellent agreement between theory and experiment. New actuation methods were used to overdrive the PZT-5H piezoelectric elements deep into the repoling range. This overdrive actuation rejuvenated the actuator elements and allowed for dramatically improved deflections with respect to configurations in previous years. Static testing demonstrated deflections in excess of ±1.6° in root-to-tip twist. Dynamic testing showed corner frequencies greater than 310 Hz. A series of wind tunnel tests at up to 180 ft/s (55 m/s, 123 mph, 107 kts, 198 kph) demonstrated excellent roll control authority, rapid manipulation of Clδ, and lift manipulation using quasi-static deflections. The paper concludes with a summary of implications for terminal guidance for drone, missile, and munition flight control in real atmospheres. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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15 pages, 5436 KiB  
Article
High Speed Microactuators for Low Aspect Ratio High Speed Micro Aircraft Surfaces
by Ronald Barrett-Gonzalez and Nathan Wolf
Actuators 2021, 10(10), 265; https://0-doi-org.brum.beds.ac.uk/10.3390/act10100265 - 13 Oct 2021
Cited by 2 | Viewed by 1774
Abstract
This paper covers a class of actuators for modern high speed, high performance subscale aircraft. The paper starts with an explanation of the challenges faced by micro aircraft, including low power, extremely tight volume constraints, and high actuator bandwidth requirements. A survey of [...] Read more.
This paper covers a class of actuators for modern high speed, high performance subscale aircraft. The paper starts with an explanation of the challenges faced by micro aircraft, including low power, extremely tight volume constraints, and high actuator bandwidth requirements. A survey of suitable actuators and actuator materials demonstrates that several classes of piezoceramic actuators are ideally matched to the operational environment. While conventional, linear actuation of piezoelectric actuators can achieve some results, dramatic improvements via reverse-biased spring mechanisms can boost performance and actuator envelopes by nearly an order of magnitude. Among the highest performance, low weight configurations are post-buckled precompressed (PBP) actuator arrangements. Analytical models display large deflections at bandwidths compatible with micro aircraft flight control speed requirements. Bench testing of an example PBP micro actuator powered low aspect ratio flight control surface displays +/−11° deflections through 40 Hz, with no occupation of volume within the aircraft fuselage and good correlation between theory and experiment. A wind tunnel model of an example high speed micro aircraft was fabricated along with low aspect ratio PBP flight control surfaces, demonstrating stable deflection characteristics with increasing speed and actuator bandwidths so high that all major aeromechanical modes could be easily controlled. A new way to control such a PBP stabilator with a Limit Dynamic Driver is found to greatly expand the dynamic range of the stabilator, boosting the dynamic response of the stabilator by more than a factor of four with position feedback system engaged. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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20 pages, 5135 KiB  
Article
Sensing, Actuation, and Control of the SmartX Prototype Morphing Wing in the Wind Tunnel
by Nakash Nazeer, Xuerui Wang and Roger M. Groves
Actuators 2021, 10(6), 107; https://0-doi-org.brum.beds.ac.uk/10.3390/act10060107 - 21 May 2021
Cited by 6 | Viewed by 2951
Abstract
This paper presents a study on trailing edge deflection estimation for the SmartX camber morphing wing demonstrator. This demonstrator integrates the technologies of smart sensing, smart actuation and smart controls using a six module distributed morphing concept. The morphing sequence is brought about [...] Read more.
This paper presents a study on trailing edge deflection estimation for the SmartX camber morphing wing demonstrator. This demonstrator integrates the technologies of smart sensing, smart actuation and smart controls using a six module distributed morphing concept. The morphing sequence is brought about by two actuators present at both ends of each of the morphing modules. The deflection estimation is carried out by interrogating optical fibers that are bonded on to the wing’s inner surface. A novel application is demonstrated using this method that utilizes the least amount of sensors for load monitoring purposes. The fiber optic sensor data is used to measure the deflections of the modules in the wind tunnel using a multi-modal fiber optic sensing approach and is compared to the deflections estimated by the actuators. Each module is probed by single-mode optical fibers that contain just four grating sensors and consider both bending and torsional deformations. The fiber optic method in this work combines the principles of hybrid interferometry and FBG spectral sensing. The analysis involves an initial calibration procedure outside the wind tunnel followed by experimental testing in the wind tunnel. This method is shown to experimentally achieve an accuracy of 2.8 mm deflection with an error of 9%. The error sources, including actuator dynamics, random errors, and nonlinear mechanical backlash, are identified and discussed. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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22 pages, 8327 KiB  
Article
Finite Time Convergence Incremental Nonlinear Dynamic Inversion-Based Attitude Control for Flying—Wing Aircraft with Actuator Faults
by Shaojie Zhang, Wuhan Han and Yuemei Zhang
Actuators 2020, 9(3), 70; https://0-doi-org.brum.beds.ac.uk/10.3390/act9030070 - 17 Aug 2020
Cited by 6 | Viewed by 2969
Abstract
In this paper, a two-loop fault-tolerant attitude control scheme is proposed for flying-wing aircraft with actuator faults. A regular nonlinear dynamic inversion (NDI) control is used in the outer attitude loop, and a finite time convergence incremental nonlinear dynamic inversion (FINDI) control combined [...] Read more.
In this paper, a two-loop fault-tolerant attitude control scheme is proposed for flying-wing aircraft with actuator faults. A regular nonlinear dynamic inversion (NDI) control is used in the outer attitude loop, and a finite time convergence incremental nonlinear dynamic inversion (FINDI) control combined with control allocation strategy is used in the inner angular rate loop. Prescribed performance bound (PPB) is designed to constrain the tracking errors within a residual set, so the prescribed system performance can be guaranteed. An optimal anti-windup (AW) compensator is introduced to solve the actuator saturation problem. Simulation results demonstrate the effectiveness of the proposed approach. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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